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United States Patent | 5,265,830 |
Allen | November 30, 1993 |
A plate projecting in an aft direction from the blunt trailing edge of a wing. The plate extends across the span of the trailing edge, and may be either planar or curved in the spanwise direction. The plate is canted to form an acute depression angle with respect to a collinear extension of the chord line of each chordwise cross section of the wing. The depression angle may vary across the span of the trailing edge. The height location of the plate relative to the trailing edge thickness may also vary in a spanwise direction. The length of the plate may be anywhere from 0.5 to 2.0 times the thickness of the trailing edge.
Inventors: | Allen; John B. (Long Beach, CA) |
Assignee: | McDonnell Douglas Corporation (Long Beach, CA) |
Appl. No.: | 823201 |
Filed: | January 21, 1992 |
Current U.S. Class: | 244/213; 244/130; 244/198; 244/215 |
Intern'l Class: | B64C 003/28 |
Field of Search: | 244/213,214,215,200,130,35 A,35 R,198,199 |
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Edwin J. Saltzman and John Hintz, "Flight Evaluation of Splitter Plate Effectiveness in Reducing Base Drag at Mach Numbers from 0.65 to 0.90", NASA Technical Memorandum X-1376 (May 1976), pp. 1-21. |